CN118129185A - Combustion nozzle and combustor - Google Patents
Combustion nozzle and combustor Download PDFInfo
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- CN118129185A CN118129185A CN202311456272.8A CN202311456272A CN118129185A CN 118129185 A CN118129185 A CN 118129185A CN 202311456272 A CN202311456272 A CN 202311456272A CN 118129185 A CN118129185 A CN 118129185A
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- fuel
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- passage
- air
- combustion
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 178
- 239000000446 fuel Substances 0.000 claims abstract description 242
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 38
- 239000012530 fluid Substances 0.000 claims description 34
- 239000007789 gas Substances 0.000 claims description 31
- 230000002093 peripheral effect Effects 0.000 claims description 31
- 239000001257 hydrogen Substances 0.000 claims description 29
- 229910052739 hydrogen Inorganic materials 0.000 claims description 29
- 238000011144 upstream manufacturing Methods 0.000 claims description 21
- 230000007423 decrease Effects 0.000 claims description 9
- 238000010791 quenching Methods 0.000 claims description 8
- 238000007599 discharging Methods 0.000 claims description 7
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 39
- 238000002347 injection Methods 0.000 description 8
- 239000007924 injection Substances 0.000 description 8
- 239000004215 Carbon black (E152) Substances 0.000 description 7
- 229930195733 hydrocarbon Natural products 0.000 description 7
- 150000002430 hydrocarbons Chemical class 0.000 description 7
- 230000000171 quenching effect Effects 0.000 description 7
- 230000006378 damage Effects 0.000 description 6
- 238000002156 mixing Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 238000004088 simulation Methods 0.000 description 6
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
- 238000005192 partition Methods 0.000 description 5
- 238000010276 construction Methods 0.000 description 4
- 150000002431 hydrogen Chemical class 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 238000009826 distribution Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 238000000638 solvent extraction Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005261 decarburization Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000009969 flowable effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The present disclosure relates to combustion nozzles and combustors. The combustion nozzle discharges compressed air and fuel to be combusted into a combustion chamber of a combustor of the gas turbine. The combustion nozzle includes an air inlet, a nozzle bore, an air passage, a fuel passage, and one or more fuel outlets. The air inlet receives the compressed air. The nozzle hole opens into the combustion chamber and discharges the compressed air. The air passage communicates between the air inlet and the nozzle hole. The fuel passage receives the fuel and discharges the fuel from one or more fuel outlets toward a flow of the compressed air discharged from the nozzle hole. The air passage includes a venturi section in which a passage cross-sectional area of the compressed air becomes relatively small. The fuel outlet is disposed in the venturi section.
Description
Technical Field
The present invention relates to a combustor of a gas turbine engine (hereinafter referred to as a "gas turbine"), a nozzle (combustion nozzle) for discharging compressed air and fuel to a combustion chamber to be combusted in the combustor, and a combustor, and more particularly, to a combustor suitable for a gas turbine (hydrogen gas turbine) capable of using hydrogen as fuel and a combustion nozzle thereof.
Background
Research and development of heat engines (such as gas turbines) using hydrogen as fuel are being advanced from the viewpoints of suppressing global warming and promoting decarburization. For example, japanese unexamined patent application publication 2016-109309 (JP 2016-109309A) proposes a combustor for a gas turbine using hydrogen and methane as fuel. The combustion field is formed by injecting methane as a main fuel from a premixed fuel combustion main burner disposed on an upstream side of a combustion cylinder constituting a combustion chamber. A plurality of diffusion combustion type reheat combustors for injecting fuel from the peripheral wall into the combustion chamber are installed in the combustion field, and hydrogen is introduced from a portion thereof. According to this configuration, the main burner is a premixed fuel combustion type burner, and thus the amount of nitrogen oxides (NOx) in the high-temperature combustion gas generated in the main combustion region on the upstream side of the combustion chamber is suppressed. Further, the distributed layout of the reheat combustors for introducing hydrogen makes the fuel concentration in each combustion region of each reheat combustor thinner, the combustion temperature of each reheat combustor is suppressed as a whole, and the generation of NOx can be suppressed. Furthermore, in this configuration, the use of a diffusion combustion reheat combustor reduces the risk of backfiring. Japanese unexamined patent application publication No. 2020-106258 (JP 2020-106258A) proposes a gas turbine using a highly reactive gas such as hydrogen as a fuel. A plurality of annular fuel injection units are concentrically arranged on an upstream end face of a combustion cylinder constituting a combustion chamber, forming a burner structure that achieves low NOx combustion and prevents backfiring and suppresses combustion dynamics. Each fuel injection unit has an annular fuel injection member having a plurality of fuel injection holes opening on an outer peripheral surface and/or an inner peripheral surface, and an annular air guide member that guides air with respect to fuel gas injected from the fuel injection holes of the annular fuel injection member. Among the plurality of circumferential partition walls and radial partition walls, at least one type of partition wall is provided, the circumferential partition walls extending radially and circumferentially partitioning gas passages of the annular fuel injection units at equal intervals, and the radial partition walls extending circumferentially and radially partitioning two adjacent annular fuel injection units. Furthermore, japanese unexamined patent application publication No. 2003-148734 (JP 2003-148734A) proposes a gas turbine apparatus. Fuel and air are delivered to the combustion chamber as a plurality of concentric jets to reduce NOx emissions and promote mixing of the fuel and air, thereby improving flame stability in the combustion chamber. The air flow is formed on the outer peripheral side of the fuel flow in the premix fuel passage, surrounding the fuel flow at the center. In this configuration, premixing makes the fuel leaner, so that low NOx can be advantageously achieved. However, a large space is required to produce a good mixing state, and as a compromise, the risk of backfiring, in which fuel backflow occurs, increases. Therefore, the configuration in which the plurality of nozzles are provided enables the fuel to burn in a narrow space in a short time, and suppresses backfiring. Although the configuration described in this document does not limit the fuel to hydrogen, this is a basic structure of a structure related to hydrogen combustion, which will be described below.
It is expected that a gas turbine (hydrogen gas turbine) using hydrogen as a fuel, which does not emit CO 2, is further widely used. For this reason, it is advantageous to downsize the gas turbine so as to be able to be installed in a vehicle such as an automobile.
When using hydrogen as fuel for a gas turbine, it is noted that hydrogen has a higher combustion temperature than the hydrocarbon fuel that has been generally used so far. In order to suppress the generation of NOx, the fuel and air are sufficiently and uniformly mixed before combustion so as not to generate a region where the fuel concentration is locally high and the combustion temperature will become high, and it is necessary to lean the total fuel concentration to maintain a low combustion temperature (more than in the case of conventional hydrocarbon fuels). In addition, hydrogen has a higher combustion rate than hydrocarbon fuels. The quenching distance of hydrogen gas (0.64 mm) is shorter than that of hydrocarbon fuel (about 2 mm). In order to suppress occurrence of backfiring, in which reverse flow of combustion occurs in the fuel passage, a different configuration from that when using conventional hydrocarbon fuel becomes necessary in a portion where fuel is injected into the combustion chamber.
In this regard, the construction of conventionally known combustors of gas turbines that can use hydrogen as a fuel is intended for medium or large power generation engines and annular combustors that produce power in excess of 1 Megawatt (MW), and is difficult to apply to small engines or annular combustors, such as those that produce power of about 1 MW. For example, in the case of a micro-hybrid combustor (for example, JP 2020-106258A) or a multi-cluster combustor known as a conventional combustor configuration of a gas turbine that can use hydrogen as a fuel, hydrogen is injected at a plurality of locations, and flames are distributed and arranged as small as possible. This suppresses the fuel concentration from becoming locally high, and the fuel in the combustion field is also in a lean state, thereby suppressing an increase in the combustion temperature. Thus, suppression of NOx generation is completed. In this case, the structure is complicated, and the number of parts is large, requiring a large space. It is difficult to achieve a miniaturized construction of such a burner. Further, when the hydrogen supply port of the combustion chamber is reduced in order to avoid backfire of the hydrogen gas of a short quenching distance, as seen in the conventional structure (JP 2020-106258A, etc.), in a configuration in which air and hydrogen gas are joined in the vicinity of the hydrogen supply port, it is difficult to sufficiently and uniformly mix the air and hydrogen gas in a small space before combustion. This requires a large space. Therefore, in order to appropriately suppress the generation of NOx in a small-sized gas turbine capable of using hydrogen as a fuel while avoiding backfiring, a combustion nozzle having a novel structure capable of sufficiently and uniformly mixing air and hydrogen in a small space before combustion and achieving combustion in a lean fuel state would be advantageous.
Disclosure of Invention
The present disclosure provides a combustion nozzle having a novel structure, which is suitable for a combustor of a small gas turbine capable of using hydrogen as a fuel.
The present disclosure also provides a combustion nozzle that can be used for a combustor such as the above-described small gas turbine, which has a novel structure that is capable of sufficiently and uniformly mixing air and hydrogen in a small space before combustion while avoiding backfiring and achieving combustion in a lean fuel state.
Further, the present disclosure provides a gas turbine combustor provided with the above combustion nozzle.
One aspect of the present disclosure is a combustion nozzle for discharging compressed air and fuel to be combusted into a combustion chamber of a combustor of a gas turbine. The combustion nozzle includes an air inlet configured to receive the compressed air, a nozzle bore leading to the combustion chamber and configured to discharge the compressed air, an air passage communicating between the air inlet and the nozzle bore, a fuel passage for receiving the fuel, and one or more fuel outlets. The fuel passage is configured to discharge the fuel from one or more fuel outlets toward a flow of the compressed air discharged from the nozzle hole. The air passage includes a venturi section in which a passage cross-sectional area of the compressed air becomes relatively small. More than one fuel outlet is provided in the venturi section.
In the above configuration, the "combustion nozzle" is a nozzle that mixes compressed air to be combusted and fuel and discharges the mixture into a combustion chamber in a combustor of a gas turbine, as described above. Here, the "air passage" is a passage for passage of air, which is defined between an "air inlet" for receiving compressed air and a "nozzle hole" leading to the combustion chamber. A "fuel passage" is a passage that receives fuel and leads it to a "fuel outlet". A "venturi section" is a section that: wherein in the air passage communicating between the air inlet and the nozzle hole, the "passage cross-sectional area" (the cross-sectional area of the region through which the fluid can flow) narrows to be relatively smaller upstream and downstream of the section. A fuel outlet, which is the outlet of the fuel passage, opens into a venturi section in the air passage and is arranged to expel fuel towards the flow of compressed air flowing therethrough. The fuel may be hydrogen.
According to the above-described configuration of the combustion nozzle of the present invention, when compressed air enters the air passage from the air inlet and is delivered from the nozzle hole, the flow rate of the air flow of the compressed air becomes high while passing through the venturi section in which the passage cross-sectional area is reduced. At this time, fuel is delivered into the flow of compressed air. Therefore, the fuel is dispersed in the air flow of the compressed air in a state where the flow rate is high. This enables the fuel to be mixed with the compressed air more evenly and thoroughly than if the fuel were simply combined with the flow of compressed air. The occurrence of a region where the fuel concentration is locally high is suppressed. A wider space is encountered when the flow of compressed air in which the fuel is dispersed flows out of the nozzle hole into the combustion chamber after passing through the venturi section. The total fuel concentration decreases. Further, when the flow rate of the compressed air increases, the fuel is delivered, so even when the fuel is hydrogen gas having a high combustion speed, backfiring into the fuel passage can be avoided. Thus, according to the above-described configuration of the present invention, in a relatively short distance in which the compressed air passes through the nozzle, that is, in a relatively small space, a state in which the compressed air and the fuel are sufficiently mixed and the fuel is lean in the combustion field can be achieved while backfiring is avoided. Therefore, the combustion temperature does not become excessively high, and the generation amount of NOx can be suppressed. Note how small the cross-sectional area of the passage in the venturi section narrows relative to the cross-sectional area of the passage upstream and downstream of the section can be determined according to applicability. In particular, when the fuel is hydrogen gas, its density is significantly lower compared to hydrocarbon fuel, and when discharged from the fuel outlet, the inertial force is smaller (momentum is weaker). Thus, in the above configuration, the one or more fuel outlets may be arranged substantially equidistantly along the circumferential direction of the air passage, so that the fuel is more reliably uniformly dispersed in the flow of the compressed air. The number of fuel outlets may be determined according to suitability. Further, in order to more reliably prevent backfiring from the combustion chamber to the fuel outlet, the fuel outlet may have an inner diameter (pore diameter) smaller than the quenching distance of the fuel. Specifically, when the fuel is hydrogen gas, the quenching distance is about 0.64mm, and thus the diameter of the fuel outlet may be, for example, 0.6mm or less.
In the above configuration, the venturi section of the air passage may include a first region in which the passage cross-sectional area gradually decreases from an upstream side of the venturi section in the air flow direction of the compressed air, and a second region in which the passage cross-sectional area gradually increases from a downstream end of the first region toward the nozzle hole. According to this configuration, the passage cross-sectional area of the air flow of the compressed air smoothly and continuously contracts and then smoothly expands. The flow of the compressed air flows over the air passage while smoothly varying the flow rate with little stagnation. Hardly any region where the fuel concentration is locally high is generated, and the fuel is more uniformly dispersed. It is desirable that the combustion temperature becomes more evenly distributed in the combustion field. In this configuration, the fuel passage may extend through a peripheral wall defining the air passage, and one or more fuel outlets may open on an inner side surface of the peripheral wall in the second region of the venturi section in which the cross-sectional area gradually increases. Alternatively, more than one fuel outlet may open on the inside surface of the peripheral wall near the downstream end of the first region of the venturi section (upstream end of the second region), i.e. at or near the portion of the venturi section where the passage cross-sectional area is smallest. According to this configuration, it is expected that the fuel will be discharged to a place where the flow rate of the air flow of the compressed air is high, and the fuel will be dispersed more uniformly. Note that the specific location of more than one fuel outlet may be determined according to suitability.
In the above configuration, a swirl nozzle may be provided on an upstream side of the venturi section of the air passage to change the flow of the compressed air into a swirl according to an alternative method, thereby dispersing the fuel more uniformly in the flow of the compressed air. The flow of compressed air becomes turbulent and passes through the venturi section that delivers fuel so that the fuel is better dispersed in the air flow during the short travel distance of the air flow. For example, such a swirl nozzle may have a center cone arranged along a central axis of the air passage in a flow direction of the compressed air, and a vane-like member extending radially from the center cone and having a surface inclined with respect to the central axis of the air passage. The flow of compressed air flows along the surface of the blade-like member (which may have a shape resembling a non-rotating auger) to generate a vortex. In the swirl nozzle having such a configuration, when the outer diameter of the center cone through which air does not flow is too large with respect to the inner diameter of the air passage, the flow velocity on the extension of the center cone will decrease, and the possibility of occurrence of reverse flow of flame from the combustion field to the center cone will increase. Thus, the ratio of the outer diameter of the central cone of the swirl nozzle to the inner diameter of the portion of the air passage in which the swirl nozzle is mounted may be lower than a predetermined value, which is adjusted so that the flow rate in the extension of the central cone does not become too slow. Alternatively, the ratio of the outer diameter of the central cone of the swirl nozzle to the inner diameter of the portion of the air passage where the swirl nozzle is mounted may be sufficiently large to avoid backflow of fluid from the combustion chamber into the air passage. According to this configuration, melting damage of the distal end of the center cone due to flame is suppressed.
Further, as a configuration to more reliably avoid the distal end of the center cone of the swirl nozzle from melting damage due to the flame, the combustion nozzle may include a center cone inner passage having a fluid outlet. The center cone internal passage passes through the center cone of the swirl nozzle along the central axis in the air passage along the flow direction of the compressed air. The fluid outlet opens at a distal end of the central cone on a downstream side of the flow of compressed air. The compressed air passes through the central cone internal passage and exits from the fluid outlet toward the combustion chamber. According to this configuration, since the air flow is also discharged from the distal end of the center cone, the flame is suppressed from reaching the distal end of the center cone. Melting damage of the distal end of the center cone is more reliably suppressed.
Note that in the above-described swirl nozzle configuration, the center cone may extend such that the distal end of the downstream side of the flow of the compressed air is located in a section of the first region in which the passage cross-sectional area of the venturi section of the air passage gradually decreases. The distal end of the downstream side of the flow of compressed air may extend to a second region in which the passage cross-sectional area of the venturi section of the air passage gradually increases. In the former case, the distal end of the central cone is arranged at a distance from the combustion field, so that melting damage of the distal end of the central cone is avoided. In the latter case, the flow rate of the air flow around the distal end of the central cone increases and backflow of combustion fluid towards the distal end of the central cone is avoided.
As another form, the combustion nozzle may include a central cone internal passage having a fluid outlet. The center cone internal passage passes through the center cone of the swirl nozzle along the center axis in the air passage along the flow direction of compressed air. The fluid outlet opens at a distal end of the central cone on the downstream side of the flow of the compressed air. The fuel passes through the central cone internal passage and the fuel is discharged from the fluid outlet toward the combustion chamber. According to this configuration, the fuel is expected to mix better with the air flow of the compressed air near the nozzle holes.
Alternatively or additionally, a further flow path of air (peripheral air flow path) may extend through the peripheral wall defining the air channel. The air outlet is provided on an inner side surface of the peripheral wall in the second region of the venturi section or on an inner side surface of the peripheral wall near the downstream end of the first region of the venturi section. The flow of compressed air flowing through the peripheral air flow path is delivered from the air outlet to the flow of compressed air passing through the air passage. According to this configuration, in the air-fuel mixture of the compressed air and the fuel that is sent to the combustion chamber, the air and the fuel are mixed better. The occurrence of uneven combustion density is suppressed. It is desirable to further suppress the amount of NOx produced. Note that the discharge direction of the fluid from the air outlet and the fuel outlet may be inclined in any direction with respect to the radial direction of the central axis of the air passage. Thus, better mixing of air and fuel is desired.
In the combustor of the gas turbine provided with the above-described combustion nozzle, a state in which the compressed air and the fuel are sufficiently mixed in the combustion chamber can be achieved, and the fuel is lean in the combustion field. Therefore, as described above, the combustion temperature does not become excessively high, and the generation amount of NOx can be suppressed. Another aspect of the present disclosure is a combustor of a gas turbine that includes a combustion nozzle for discharging compressed air and fuel to be combusted into a combustion chamber. The combustion nozzle includes an air inlet configured to receive the compressed air, a nozzle hole leading to the combustion chamber and configured to discharge the compressed air, an air passage communicating between the air inlet and the nozzle hole, a fuel passage for receiving the fuel, and a fuel outlet. The fuel passage is configured to discharge the fuel from the fuel outlet toward a flow of the compressed air discharged from the nozzle hole. The air passage includes a venturi section in which a passage cross-sectional area of the compressed air becomes relatively small. The fuel outlet is disposed in the venturi section. In the burner of the present invention, the combustion nozzle may have various characteristic configurations as described above. Such a case is also included in the scope of the present invention.
Thus, the combustion nozzle of the gas turbine combustor of the present invention described above is capable of achieving a sufficiently uniform mixing of fuel and air streams and a rarefaction of fuel concentration in a short distance when the air streams of compressed air and fuel are delivered to the combustion chamber. Such a combustion nozzle can be used as a combustion nozzle of a combustor of a small-sized gas turbine, and can avoid backfiring and suppress the generation of NOx even when a fuel such as hydrogen gas having a high combustion temperature is used. The combustion nozzle and the combustor equipped with the same according to the present invention can be used for a gas turbine using hydrogen as a fuel, which is downsized so as to be mountable in a vehicle such as an automobile. Therefore, hydrogen gas turbines are expected to find wider application.
Other objects and advantages of the present invention will become apparent from the following description of the preferred embodiments of the present invention.
Drawings
Features, advantages, and technical and industrial significance of exemplary embodiments of the present invention will be described below with reference to the accompanying drawings, in which like numerals denote like elements, and in which:
FIG. 1A is a schematic cross-sectional view of a combustor of a gas turbine with a combustion nozzle according to an embodiment applied;
FIG. 1B is a schematic perspective view of a combustion nozzle according to an embodiment;
FIG. 1C is a schematic cross-sectional view of a combustion nozzle (taken along line 1C-1C in FIG. 1B) according to an embodiment;
FIG. 1D is a schematic perspective view of a swirl nozzle disposed within an air passage of a combustion nozzle of an embodiment;
FIG. 2 is an enlarged schematic cross-sectional view of a nozzle bore and vicinity of a venturi section of a combustion nozzle according to the present embodiment;
FIG. 3A is a schematic cross-sectional view of a combustion nozzle according to an embodiment, illustrating simulation results of velocity distribution of fluid discharged from a nozzle orifice when an inside-to-outside ratio (R1/R2) is 0.4, wherein a flow rate is represented by intensity of luminance in the illustration;
FIG. 3B is a schematic cross-sectional view of a combustion nozzle according to an embodiment, illustrating simulation results of velocity profile of fluid discharged from a nozzle orifice when an inside-to-outside ratio exceeds 0.4, wherein the flow rate is represented in the illustration by intensity of luminance;
FIG. 4A is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a fuel outlet is provided in a region in which a passage cross-sectional area of a venturi section gradually increases toward a nozzle orifice;
FIG. 4B is a schematic cross-sectional view of a variation of the combustion nozzle according to an embodiment, illustrating an example in which the fuel outlet is provided near (on the upstream side of) a position where the passage cross-sectional area of the venturi section is smallest;
FIG. 4C is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a region of the venturi section where the passage cross-sectional area is smallest is formed to have a certain length in the flow direction of the fluid;
FIG. 4D is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which the nozzle orifice is disposed without a gradual increase in passage cross-sectional area from a location where the passage cross-sectional area of the venturi section is minimal;
FIG. 4E is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a center cone of a swirl nozzle disposed in an air passage protrudes to a position where a passage cross-sectional area of a venturi section is minimal;
FIG. 5A is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a center cone of a swirl nozzle disposed in an air passage protrudes to a position where a passage cross-sectional area of a venturi section is smallest, and a fuel passage is formed through not only a peripheral wall portion of the combustion nozzle but also the center cone such that fuel is injected from a distal end of the center cone as well;
FIG. 5B is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a center cone of a swirl nozzle disposed in an air passage protrudes to a position where a passage cross-sectional area of a venturi section is smallest, and a fuel passage is formed through the center cone such that fuel is injected from a distal end of the center cone;
FIG. 5C is a schematic cross-sectional view of a variation of a combustion nozzle according to an embodiment, illustrating an example in which a center cone of a swirl nozzle disposed in an air passage protrudes to a position where a passage cross-sectional area of a venturi section is smallest, and a fuel passage is formed through the center cone such that fuel is injected in a circumferential direction from a fuel outlet provided near a distal end of the center cone;
FIG. 6 is a schematic cross-sectional view of a further variation of a combustion nozzle according to an embodiment, illustrating an example in which vane-like members of a swirl nozzle arranged in an air passage are provided at air inlets perforated in a peripheral wall portion of the combustion nozzle;
FIG. 7A is a schematic cross-sectional view of a further variation of a combustion nozzle according to an embodiment, illustrating an example in which an air passage is also formed through a center cone of a swirl nozzle such that air is also discharged from a distal end of the center cone;
FIG. 7B is a schematic cross-sectional view of a combustion nozzle according to an embodiment, illustrating simulation results of temperature distribution of fluid around a nozzle orifice when the nozzle is formed such that air is also expelled from the distal end of the center cone, where the height of the temperature is represented by the intensity of the luminance;
FIG. 7C is a schematic cross-sectional view of a combustion nozzle according to an embodiment, illustrating simulation results of temperature distribution of fluid around a nozzle orifice when air is not discharged from a distal end of a center cone, wherein a height of the temperature is represented by intensity of luminance;
FIG. 8A is a schematic cross-sectional view of another variation of a combustion nozzle according to an embodiment, illustrating an example in which an air passage is also formed through a nozzle peripheral wall portion such that not only fuel but also air is discharged from the peripheral wall at a venturi section;
FIG. 8B is a cross-sectional view, as viewed from a direction perpendicular to the flow direction of the air passage in the venturi section near the nozzle hole, illustrating the layout of the fuel outlets and the air outlets, showing the case where the fuel outlets and the air outlets are each alternately arranged along the circumferential direction of the nozzle hole and extend in a substantially radial direction from the center of the nozzle hole;
FIG. 8C is a cross-sectional view from a direction perpendicular to the flow direction of the air passage in the venturi section near the nozzle hole, illustrating the layout of the fuel outlets and the air outlets, showing the case where the fuel outlets and the air outlets are each alternately arranged along the circumferential direction of the nozzle hole and extend obliquely from the center of the nozzle hole with respect to the radial direction;
FIG. 9A is a schematic cross-sectional view of a further variation of a combustion nozzle according to an embodiment, which is an example formed such that air is further discharged from the outer periphery of the nozzle hole; and
Fig. 9B is a schematic front view of the ring member in which discharge holes (viewed from a direction perpendicular to the flow of fluid from the nozzle holes) for discharging air from the outer periphery of the nozzle holes are arranged.
Detailed Description
Basic construction of burner and combustion nozzle
According to embodiments, the combustion nozzle may be advantageously used in a combustor of a gas turbine fueled by hydrogen or other substances that are lighter in mass and burn higher temperatures than the hydrocarbon-based materials used heretofore. As shown in fig. 1A, in a combustor 1 of a gas turbine, a combustion nozzle 2 is mounted in an opening portion 3o in a casing 3h of a combustion chamber 3 defining a combustion field 3 f. In short, in the combustion nozzle 2, the compressed air PA enters from a compressor (omitted in the drawing) connected to a turbine (omitted in the drawing) through a compressed air supply ring 4, the compressed air supply ring 4 being annular and defined on the outer periphery of the combustion chamber 3. Further, the fuel F flows in from a fuel tank (omitted from the figure) through a fuel supply line 2 a. These are then mixed and fed to the combustion field 3f for combustion.
In the basic configuration of the combustion nozzle 2, as shown in fig. 1B and 1C, the peripheral wall portion 2B is substantially cylindrical and extends in the axial direction of the cylinder at the center thereof, and defines an air passage 2x that opens at a nozzle hole 2d, the nozzle hole 2d being mounted in an opening portion 3o of the combustion chamber. The combustion nozzle 2 sucks in the compressed air PA from an air inlet 4a formed on the upstream side of the peripheral wall portion 2b, and delivers the air from the nozzle hole 2d to the combustion field 3f. The cross section of the air passage 2x in the direction perpendicular to the fluid flow direction may be substantially circular, but is not limited thereto. Furthermore, the fuel passageFormed inside the peripheral wall portion 2b, passing through the peripheral wall portion 2b, and opening at a fuel outlet 2F on the inner wall of the peripheral wall portion 2b, through which fuel F supplied through the fuel supply line 2a flows/>The fuel is injected toward the air flow of the compressed air PA flowing in the air passage 2 x. The fuel outlets 2f are generally arranged at a plurality of portions at substantially equidistant intervals along the circumferential direction of the air passage 2 x. Note that in the peripheral wall portion 2b, the fuel passage/>Through the portion through which no air flow path passes so as not to interfere with the air flow path from the air inlet 4a to the air passage 2 x. Furthermore, the swirl nozzle 5 may be arranged within the air passage 2x defined by the peripheral wall portion 2b, as schematically shown in fig. 1D. The swirl nozzle 5 has a center cone 5c extending along a substantially middle portion of the air passage 2x, and a plurality of vane-like members 5w extending radially around the center cone 5 c. The swirl nozzle 5 has a shape resembling a non-rotating auger. In the swirl nozzle 5, the surface of the vane-like member 5w is inclined with respect to the central axis of the air passage. Therefore, when the flow of the compressed air flows along the surface of the blade-like member 5w, the flow direction thereof is rotated, forming a vortex.
Specifically, in the combustion nozzle 2 according to the present embodiment, as shown in fig. 1C, a "venturi section" 2e, i.e., a section in which the cross-sectional area of the passage (the cross-sectional area in the direction perpendicular to the fluid flow direction in the fluid flowable region) is reduced to be relatively smaller than upstream and downstream of the section, is formed in the air passage 2 x. The fuel outlet 2f is arranged in the venturi section 2 e. In short, as described in the "summary of the invention", this configuration increases the flow rate of the compressed air PA as it passes through the venturi section 2 e. At this point in time, fuel F is delivered into the flow of compressed air PA. Therefore, the fuel F is dispersed in the air flow of the compressed air PA in a state where the flow rate thereof is high. This enables the fuel to be more uniformly and thoroughly mixed with the compressed air in a shorter travel distance than if the fuel were simply merged with the flow of compressed air. The occurrence of a region where the fuel concentration is locally high is suppressed. The flow of compressed air PA in which the fuel F is dispersed has passed through the venturi section 2e and flows out from the nozzle holes 2d to the combustion field 3F in the combustion chamber, the flow of compressed air being spread over a wide space. This reduces the total fuel concentration. Further, the fuel outlet 2F is provided at a position where the flow rate of the compressed air PA increases, to which the fuel F is delivered. This makes it possible to avoid backfiring into the fuel passage 2 phi even when the fuel is hydrogen gas having a short quenching distance. Thus, according to the configuration of the present embodiment, the fuel is dispersed in the air at the nozzle holes 2d in a more uniform and lean manner while backfiring is avoided. This can suppress the amount of NOx produced.
According to the present embodiment, the ratio of the passage cross-sectional area of the venturi section 2e with respect to the upstream and downstream regions of the venturi section 2e or the inner diameter ratio of the venturi section 2e with respect to the upstream and downstream regions of the venturi section 2e and the length of the venturi section 2e in the flow direction in the air passage 2x can be determined so that the fuel is more uniformly dispersed in the flow of the compressed air PA. Referring to fig. 2, the venturi section 2e may be sized such that the passage cross-sectional area (pi X 2/4) of a portion of the venturi section 2e where the flow passage cross-sectional area is smallest (minimum diameter X) is significantly smaller than the passage cross-sectional area (pi (4 YYr-Yr 2)/4) of the upstream side of the venturi section 2 e. Typically, the ratio of the minimum diameter X of the venturi section 2e to the inner diameter Y of the upstream side of the venturi section 2e may be 40% to 80%. Further, as shown herein, the inner diameter and the passage cross-sectional area of the venturi section 2e gradually decrease from the upstream side (the first region 2 ei) of the venturi section 2e in the flow direction of the fluid and reach the minimum diameter portion. Thereafter, the inner diameter and the passage cross-sectional area gradually increase toward the nozzle hole 2d (second region 2 eii). Thus, the flow rate of the air flow of the compressed air is smoothly increased and decreased without stagnation.
The fuel outlet 2f provided in the venturi section 2e may be provided at a position where the flow rate of the flow of the compressed air is high. The arrangement position of the fuel outlets 2f may be determined so that the fuel is more uniformly distributed in the flow of the compressed air PA. The fuel outlet 2f may be provided near the smallest diameter portion of the venturi section 2 e. Specifically, near the minimum diameter portion of the venturi section 2e is a section pt upstream and downstream of the minimum diameter portion in fig. 2. The length pt of the nearby section may be a section satisfying pt/p.ltoreq.60% with respect to the length p of the venturi section 2e (the length of the section having an inner diameter smaller than Y).
The pore diameter of the fuel outlet 2f is preferably set to be smaller than the quenching distance of the fuel to suppress backfiring of the post-combustion fluid in the fuel passage. When the fuel is hydrogen, the quenching distance is 0.64mm. For example, the aperture of the fuel outlet may be smaller, such as below 0.6 mm.
Further, when the fuel is a light substance such as hydrogen, the inertial force is small (momentum is weak) when discharged from the fuel outlet. Simply discharging fuel from one edge of the air stream would require time to disperse as a whole. Thus, as shown, the fuel outlets may be disposed at portions substantially equidistant along the circumferential direction of the flow of compressed air, so that the fuel is more uniformly dispersed in the flow of air thereof.
Further, as described above, the swirl nozzle 5 that rotates the air flow direction in the air passage 2x is provided, swirling the air flow of the compressed air, and passing through the venturi section 2e. The fuel will be more evenly distributed in the flow of compressed air. In this swirl nozzle 5, as described above, the center cone 5c extends in the substantially middle portion of the air passage 2 x. In this regard, according to the study of the inventors of the present embodiment, when the ratio of the cross-sectional area or diameter R1 of the center cone 5c to the passage cross-sectional area or inner diameter R2 of the air passage 2x is too large, the flow rate of the fluid on the extension of the center cone 5c in the nozzle hole 2d is relatively lower than that of the surrounding fluid. Thus, heat from the combustion field 3f can easily reach the distal end of the center cone 5 c. As shown in fig. 3A and 3B, according to the simulation performed by the inventors of the present embodiment, when the ratio R1/R2 (referred to as "inside-outside ratio (boss ratio)") of the outer diameter R1 of the center cone 5c with respect to the inner diameter R2 of the air passage 2x on the upstream side of the venturi section 2e (i.e., Y in fig. 2) is smaller than 0.4, any region where the flow velocity decreases on the extension line of the center cone 5c in the nozzle hole 2d is hardly observed, as shown in fig. 3A. When the inside-outside diameter ratio R1/R2 exceeds 0.4, as shown in fig. 3B, a region of reduced flow velocity occurs on the extension line of the center cone 5c in the nozzle hole 2 d. The reverse flow rf of combustion fluid from the combustion field 3f to the central cone 5c is more likely to occur. Thus, in the combustion nozzle according to the present embodiment, the outer diameter of the center cone of the swirl nozzle may be designed so that the inside-outside diameter ratio R1/R2 is not excessively large (for example, 0.4 or less (0.16 or less in terms of the cross-sectional area ratio)).
Construction example of combustion nozzle
The specific configuration of the present embodiment can be modified in various ways while satisfying the above-described preferable requirements. For example, in addition to opening in a portion of the venturi section 2e of substantially the smallest diameter as shown in fig. 1C, as long as the flow rate of the flow of the compressed air is relatively high, as shown in fig. 4A, the fuel outlet 2f may be opened in a second region 2eii in which the passage cross-sectional area gradually increases from the portion of the venturi section 2e of the smallest diameter to the nozzle hole 2 d. Alternatively, as shown in fig. 4B, the fuel outlet 2f may be opened in a first region 2ei in which the passage cross-sectional area gradually decreases in the vicinity of the smallest diameter portion of the venturi section 2 e. Furthermore, as shown in fig. 4C, the region 2et in which the passage cross-sectional area of the venturi section 2e is smallest may have a length in the flow direction to some extent. Alternatively, as shown in fig. 4D, the nozzle hole 2D may be formed to be directly opened from the smallest diameter portion of the venturi section 2e (the second region 2eii in which the passage cross-sectional area gradually increases is not formed). Further, as shown in fig. 4E, the center cone 5c of the swirl nozzle may extend to the smallest diameter portion of the venturi section 2E to such an extent that the dispersion of fuel in the mixed fluid discharged from the nozzle hole 2d is not reduced. This increases the flow rate in the venturi section. The backflow of fluid from the combustion field 3f to the nozzle holes 2d can be made less likely to occur.
Furthermore, when the swirl nozzle 5 having the center cone 5c is disposed in the air passage 2x, the center cone 5c extends to the venturi section 2e as shown in fig. 5A. Fuel passageThrough the central cone 5c and a fuel outlet 2f is formed at its distal end. The air and fuel are mixed better, thereby reducing the amount of NOx produced. Note that when the central cone 5c extends to the venturi section 2e in the air channel 2x, the fuel channel/>May be formed only in the center cone 5c (no fuel passage/> is formed in the peripheral wall portion 2b of the nozzle) And the fuel outlet 2f may be open at its distal end as shown in fig. 5B. In this case, the fuel passage/>, is facilitatedIs formed by the steps of (a). Note that the fuel outlet 2f that opens at the distal end of the center cone 5C may open along the outer periphery of the distal end thereof so as to radially inject fuel near the distal end of the center cone 5C, as shown in fig. 5C.
Note that the vane-like member 5w of the swirl nozzle 5 for rotating the air flow direction may be provided at the air inlet 4a as shown in fig. 6. The configuration in which the blade-like member 5w is provided at the air inlet 4A may also be applied to the configurations shown in fig. 4A to 5C.
Additional air passage
In the combustion nozzle of the present embodiment described above, additional air passages as described below may be formed.
First, as shown in fig. 7A, when the swirl nozzle 5 having the center cone 5c is provided in the air passage 2x, the air passage may be further formed to pass through the center cone 5c in the axial direction thereof, and the compressed air may flow out from the distal end (2 g) of the center cone 5 c. According to the simulation performed by the inventors of the present embodiment, when no compressed air is discharged from the distal end of the center cone 5C, the temperature of the center cone 5C becomes relatively high, as shown in fig. 7C. When the compressed air is discharged from the distal end of the center cone 5c, the temperature of the center cone 5c becomes relatively low, as shown in fig. 7B. Accordingly, in the present embodiment, as also shown in fig. 7A, discharging the compressed air from the distal end of the center cone 5c protects the distal end of the center cone 5c, which is easily exposed to high temperature, from combustion heat, and reduces the possibility of melting damage.
Further, as shown in fig. 8A, in the combustion nozzle 2, an additional air passage (air passage inside the peripheral wall portion) 4b may pass through the peripheral wall portion 2b defining the air passage 2x, and the fuel passageParallel. The air outlets 2g are arranged in a circumferential direction with respect to the fuel outlets 2 f. Regarding the air flow of the compressed air flowing through the air passage 2x, the air flow is discharged from the air outlet 2g therearound. With this configuration, the fuel F discharged from the fuel outlet 2F can be expected to be more uniformly dispersed in the flow of the compressed air. In this regard, the fuel outlets 2f and the air outlets 2g in the venturi section 2e may be alternately arranged in the circumferential direction. As shown in fig. 8B, the direction may be radially toward the center of the air passage 2 x. Alternatively, as shown in fig. 8C, the orientation thereof may be alternatively inclined toward the center of the air passage 2x with respect to the radial direction. Therefore, in the flow of the compressed air in the air passage 2x, the flow of fuel from the fuel outlet 2f collides with the flow of air from the air outlet 2 g. The fuel and air are mixed more uniformly.
As another form, in order to discharge the compressed air from the outer periphery of the nozzle hole 2d of the combustion nozzle 2 to the combustion field 3f, an exhaust ring 6 may be mounted to the outer periphery of the combustion nozzle 2 as shown in fig. 9A such that the compressed air PA flows out from the exhaust hole 6a perforated in the circumferential direction of the ring 6 as shown in fig. 9B. According to this configuration, the air and the fuel are mixed more uniformly. The amount of NOx produced is suppressed. It is also possible to obtain a cooling effect on the peripheral wall portion of the nozzle. This effect is particularly advantageous when the fuel is hydrogen, due to its high combustion temperature. The exhaust ring 6 is simply a ring provided with through holes and can therefore be added at relatively low cost.
Therefore, in the combustion nozzle having the above-described series of structures, the flow of the compressed air introduced into the nozzle is temporarily restricted to increase the flow rate. Fuel is then injected there (e.g., from around the air stream). Thus, the delivery to the combustion field is performed in a state of a more uniform mixture of air and fuel over a relatively short distance. The air-fuel mixture is combusted in a leaner fuel state. In the case of a burner or combustion nozzle used in a conventional hydrogen gas turbine, the fuel is combined with a stream of compressed air and then transported a significant distance before entering the combustion field in order to mix the air and fuel to the extent that NOx production is properly controlled. Optionally, the portion into which the fuel and air are introduced is subdivided so that the flame generated in the combustion field is a micro flame to suppress the combustion temperature to a low temperature. Therefore, since a large number of fuel supply ports and air supply ports are provided, the nozzle occupies a large space. It is difficult to reduce the size of the combustion nozzle or burner. In contrast, according to the configuration of the present embodiment, as described above, the fuel and the air are sufficiently uniformly mixed while traveling a relatively short distance. In the combustion field, the occurrence of a region where the fuel concentration is locally high is suppressed. The total fuel concentration also remains low. The fuel temperature does not become excessively high locally or as a whole. The suppression of the NOx production amount is achieved. In addition, the compressed air flow is compressed before reaching the nozzle holes and is thus conveyed to the combustion field, whereby a backflow (backfire) of the fluid from the combustion field is less likely to occur. Thermal damage (melt damage) of the nozzle member is suppressed. According to the configuration of the present embodiment, the combustion nozzle can be made relatively compact, the fuel and air can be uniformly mixed to make the mixture thinner, while suppressing backfiring, so that the amount of NOx generation can be suppressed. The combustion nozzle according to the present embodiment can be particularly advantageously used in a combustor of a small gas turbine capable of using hydrogen as a fuel.
While the embodiments of the present invention have been described above, various modifications and changes will readily occur to those skilled in the art. The present invention is not limited to the above-exemplified embodiments and can be applied to various types of devices without departing from the concept of the present invention.
Claims (15)
1. A combustion nozzle configured to discharge compressed air and fuel to be combusted into a combustion chamber of a combustor of a gas turbine, the combustion nozzle characterized by comprising:
An air inlet configured to receive the compressed air;
a nozzle hole that opens into the combustion chamber and that is configured to discharge the compressed air;
an air passage communicating between the air inlet and the nozzle hole;
A fuel passage for receiving the fuel; and
One or more fuel outlets, where
The fuel passage is configured to discharge the fuel from the one or more fuel outlets toward the flow of the compressed air discharged from the nozzle hole,
The air passage includes a venturi section in which a passage cross-sectional area of the compressed air becomes relatively small, and
The one or more fuel outlets are disposed in the venturi section.
2. The combustion nozzle of claim 1 wherein the one or more fuel outlets are disposed substantially equidistant along a circumferential direction of the air passage.
3. The combustion nozzle according to claim 1 or 2, characterized in that
The venturi section comprises
A first region in which the passage cross-sectional area gradually decreases from an upstream side of the venturi section in a flow direction of the compressed air, and
A second region in which the passage cross-sectional area gradually increases from a downstream end of the first region toward the nozzle hole.
4. A combustion nozzle as claimed in claim 3, wherein:
The fuel passage extends through a peripheral wall defining the air passage; and
The one or more fuel outlets open on an inside surface of the peripheral wall in the second region of the venturi section.
5. A combustion nozzle as claimed in claim 3, wherein:
The fuel passage extends through a peripheral wall defining the air passage; and
The one or more fuel outlets open on an inside surface of the peripheral wall near the downstream end of the first region of the venturi section.
6. The combustion nozzle of claim 1, further comprising a swirl nozzle disposed on an upstream side of the venturi section of the air passage and configured to change the flow of the compressed air to a swirl.
7. The combustion nozzle of claim 6, wherein:
The vortex nozzle comprises
A center cone arranged along a center axis of the air passage in a flow direction of the compressed air, and
A blade-like member extending radially from the center cone and including a surface inclined with respect to the center axis of the air passage; and
The compressed air flows along the surface of the blade-like member to generate the vortex.
8. The combustion nozzle of claim 7, wherein a ratio of an outer diameter of the center cone of the swirl nozzle to an inner diameter of a portion of the air passage where the swirl nozzle is mounted is below a predetermined value.
9. The combustion nozzle of claim 7 wherein the ratio of the outer diameter of the center cone of the swirl nozzle to the inner diameter of the portion of the air passage where the swirl nozzle is mounted is sufficiently large to avoid backflow of fluid from the combustion chamber into the air passage.
10. The combustion nozzle of claim 7 comprising a central cone internal passage comprising a fluid outlet,
Wherein the center cone internal passage passes through the center cone of the swirl nozzle along the center axis, and the fluid outlet is open at a distal end of the center cone on a downstream side of the flow of the compressed air such that the compressed air passes through the center cone internal passage, and the compressed air is discharged from the fluid outlet toward the combustion chamber.
11. The combustion nozzle of claim 7, wherein:
the venturi section comprises
A first region in which the passage cross-sectional area gradually decreases from the upstream side of the venturi section in the flow direction of the compressed air, and
A second region in which the passage cross-sectional area gradually increases from a downstream end of the first region toward the nozzle hole; and
The center cone of the swirl nozzle extends such that a distal end of the center cone on a downstream side of the flow of the compressed air extends to a position of the downstream end of the first region.
12. The combustion nozzle of claim 7 further comprising a central cone internal passage including a fluid outlet,
Wherein the center cone internal passage passes through the center cone of the swirl nozzle along the center axis, and the fluid outlet is open at a distal end of the center cone on a downstream side of the flow of the compressed air such that the fuel passes through the center cone internal passage, and the fuel is discharged from the fluid outlet toward the combustion chamber.
13. The combustion nozzle of claim 1 wherein the inner diameter of the one or more fuel outlets is less than the quench distance of the fuel.
14. The combustion nozzle of claim 13 wherein the fuel is hydrogen.
15. A combustor of a gas turbine, the combustor characterized by comprising a combustion nozzle for discharging compressed air and fuel to be combusted into a combustion chamber, wherein:
The combustion nozzle comprises
An air inlet configured to receive the compressed air,
A nozzle hole opening into the combustion chamber and configured to discharge the compressed air,
An air passage communicating between the air inlet and the nozzle hole,
A fuel passage for receiving the fuel, and
A fuel outlet;
the fuel passage is configured to discharge the fuel from the fuel outlet toward a flow of the compressed air discharged from the nozzle hole;
the air passage includes a venturi section in which a passage cross-sectional area of the compressed air becomes relatively small; and
The fuel outlet is disposed in the venturi section.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2022-193746 | 2022-12-02 | ||
| JP2022193746A JP2024080498A (en) | 2022-12-02 | 2022-12-02 | Combustor appropriate to hydrogen gas turbine, and its combustion nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118129185A true CN118129185A (en) | 2024-06-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311456272.8A Pending CN118129185A (en) | 2022-12-02 | 2023-11-03 | Combustion nozzle and combustor |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20240183537A1 (en) |
| EP (1) | EP4379261A1 (en) |
| JP (1) | JP2024080498A (en) |
| CN (1) | CN118129185A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3912164A (en) * | 1971-01-11 | 1975-10-14 | Parker Hannifin Corp | Method of liquid fuel injection, and to air blast atomizers |
| US4845952A (en) * | 1987-10-23 | 1989-07-11 | General Electric Company | Multiple venturi tube gas fuel injector for catalytic combustor |
| DE4330083A1 (en) * | 1993-09-06 | 1995-03-09 | Abb Research Ltd | Method of operating a premix burner |
| JP3960166B2 (en) | 2001-08-29 | 2007-08-15 | 株式会社日立製作所 | Gas turbine combustor and operation method of gas turbine combustor |
| EP1485593A1 (en) * | 2002-02-22 | 2004-12-15 | Catalytica Energy Systems, Inc. | Catalytically piloted combustion system and methods of operation |
| US7059135B2 (en) * | 2004-08-30 | 2006-06-13 | General Electric Company | Method to decrease combustor emissions |
| GB0625016D0 (en) * | 2006-12-15 | 2007-01-24 | Rolls Royce Plc | Fuel injector |
| US8215116B2 (en) * | 2008-10-02 | 2012-07-10 | General Electric Company | System and method for air-fuel mixing in gas turbines |
| JP5581979B2 (en) * | 2010-11-04 | 2014-09-03 | 株式会社Ｉｈｉ | Combustion heater |
| JP2016109309A (en) | 2014-12-02 | 2016-06-20 | 川崎重工業株式会社 | Combustor for gas turbine, and gas turbine |
| JP7336848B2 (en) | 2018-12-28 | 2023-09-01 | 川崎重工業株式会社 | Combustion device |
-
2022
- 2022-12-02 JP JP2022193746A patent/JP2024080498A/en active Pending
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2023
- 2023-10-31 US US18/498,387 patent/US20240183537A1/en active Pending
- 2023-11-03 CN CN202311456272.8A patent/CN118129185A/en active Pending
- 2023-11-10 EP EP23209242.9A patent/EP4379261A1/en active Pending
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| JP2024080498A (en) | 2024-06-13 |
| US20240183537A1 (en) | 2024-06-06 |
| EP4379261A1 (en) | 2024-06-05 |
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